Research On Propeller UAV Rocket Booster Launching Control And Influential Factors

The launching of UAV is a very important stage during all phases of flight, and to make sure the taking-off task steadily and securely is an emphasis and difficulty of researching the UAV. In this paper, taking the folding-wings, container-type launching and rockets booster launching UAV as the research object, the influence factors are studied, such as the engine clutch time and the deployment time of folding-wings; and to stabilize the attitude in launching process, the control system via PID and adaptive control method is designed, which is feasible validated by simulation.Firstly, the mechanism modeling method is applied to analyze the force of the launching process in this paper. And according to whether the wings fold, the modeling processes are divided into the material point modeling and rigid-body modeling. Based on the idea of modularization, respectively, the gravity model, engine thrust model, rocket thrust model and aerodynamic forces and torque model, etc, are established. On this basis, the mathematical model of launching process through Matlab is established and linearized.Then, in order to guarantee the stability and safety of the flight in launching process, the factors of launching process are analyzed. Based on the multi-rigid-body physical structure, the factors are classified into four types: the inherent factors of UAV, the rocket factor, the factors of launcher and external factors. On account of the UAV with folding wings and container launching, taking the safety height and speed as the aim, the engine clutch time, the deployment time of folding-wings, the rocket installation position factor, the launching angle and the wind disturbance are analyzed.Next, the control system of launching process is designed. The PID and adaptive control method are adopted. Firstly, the PID control is used to design the flight control system, and using the SPSA method simplifies the parameter adjustment process. Then adaptive control method is adopted to design the attitude control system. Furthermore, flight situation of two methods is tested respectively.Finally, Matlab/GUI software is applied to design the UAV flying interface, which realized the simulink model and GUI connect seamlessly. The simulation results show that the interface can realize the quantity of state and control real-time display, and on-line tunes the controls parameter, which verifys the feasibility of the flying system.